FR3078947B1 - AIRCRAFT PROPULSION SYSTEM COMPRISING A DUAL-FLOW TURBOREACTOR AND A REDUCED AIR TAKE-OFF SYSTEM - Google Patents
AIRCRAFT PROPULSION SYSTEM COMPRISING A DUAL-FLOW TURBOREACTOR AND A REDUCED AIR TAKE-OFF SYSTEM Download PDFInfo
- Publication number
- FR3078947B1 FR3078947B1 FR1852135A FR1852135A FR3078947B1 FR 3078947 B1 FR3078947 B1 FR 3078947B1 FR 1852135 A FR1852135 A FR 1852135A FR 1852135 A FR1852135 A FR 1852135A FR 3078947 B1 FR3078947 B1 FR 3078947B1
- Authority
- FR
- France
- Prior art keywords
- perforated grid
- propulsion system
- air
- shutter
- dual
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
- F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/16—Aircraft characterised by the type or position of power plant of jet type
- B64D27/18—Aircraft characterised by the type or position of power plant of jet type within or attached to wing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0618—Environmental Control Systems with arrangements for reducing or managing bleed air, using another air source, e.g. ram air
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/024—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising cooling means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
- B64D2033/0273—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/605—Venting into the ambient atmosphere or the like
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
L'invention concerne un système de propulsion (120) pour un aéronef comportant un système d'air (206), ledit système de propulsion (120) comportant : - un carénage (112) présentant une grille ajourée (114), - un turboréacteur double flux (110) avec un étage de compression (202) et une veine secondaire (204), et - un système de prélèvement d'air (200) comportant un échangeur thermique (208), une canalisation chaude (250) connectée entre l'étage de compression (202) et le système d'air (206), et traversant l'échangeur thermique (208), et une canalisation froide (252) connectée entre la veine secondaire (204) et la grille ajourée (114), et traversant l'échangeur thermique (208). Le système de prélèvement d'air (200) comporte un volet (210) qui est arrangé au niveau de la grille ajourée (114) et qui est déplacé par un moteur (212) entre une position ouverte dans laquelle le volet (210) n'obture pas les trous de la grille ajourée (114) et une position fermée dans laquelle le volet (210) obture les trous de la grille ajourée (114). L'intégration de la fonction d'évacuation et de régulation au niveau de la grille ajourée (114) permet un gain de place, ce qui facilite l'intégration du système de prélèvement d'air (200) dans le système de propulsion (120).The invention relates to a propulsion system (120) for an aircraft comprising an air system (206), said propulsion system (120) comprising: - a fairing (112) having a perforated grid (114), - a turbojet double flow (110) with a compression stage (202) and a secondary stream (204), and - an air bleed system (200) comprising a heat exchanger (208), a hot pipe (250) connected between the 'compression stage (202) and the air system (206), and passing through the heat exchanger (208), and a cold pipe (252) connected between the secondary stream (204) and the perforated grid (114), and passing through the heat exchanger (208). The air sampling system (200) comprises a shutter (210) which is arranged at the level of the perforated grid (114) and which is moved by a motor (212) between an open position in which the shutter (210) n 'not closes the holes of the perforated grid (114) and a closed position in which the shutter (210) closes the holes of the perforated grid (114). The integration of the evacuation and regulation function at the level of the perforated grid (114) saves space, which facilitates the integration of the air sampling system (200) in the propulsion system (120 ).
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1852135A FR3078947B1 (en) | 2018-03-13 | 2018-03-13 | AIRCRAFT PROPULSION SYSTEM COMPRISING A DUAL-FLOW TURBOREACTOR AND A REDUCED AIR TAKE-OFF SYSTEM |
US16/271,300 US20190285000A1 (en) | 2018-03-13 | 2019-02-08 | Propulsion system of an aircraft comprising a dual-flow jet engine and an air-drawing system with reduced bulk |
EP19156326.1A EP3539873B1 (en) | 2018-03-13 | 2019-02-11 | Propulsion system of an aircraft comprising a dual-flow jet engine and a compact air sampling system |
CN201910180585.2A CN110271676A (en) | 2018-03-13 | 2019-03-11 | Propulsion system and aircraft including it |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1852135A FR3078947B1 (en) | 2018-03-13 | 2018-03-13 | AIRCRAFT PROPULSION SYSTEM COMPRISING A DUAL-FLOW TURBOREACTOR AND A REDUCED AIR TAKE-OFF SYSTEM |
FR1852135 | 2018-03-13 |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3078947A1 FR3078947A1 (en) | 2019-09-20 |
FR3078947B1 true FR3078947B1 (en) | 2020-03-13 |
Family
ID=62067728
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1852135A Expired - Fee Related FR3078947B1 (en) | 2018-03-13 | 2018-03-13 | AIRCRAFT PROPULSION SYSTEM COMPRISING A DUAL-FLOW TURBOREACTOR AND A REDUCED AIR TAKE-OFF SYSTEM |
Country Status (4)
Country | Link |
---|---|
US (1) | US20190285000A1 (en) |
EP (1) | EP3539873B1 (en) |
CN (1) | CN110271676A (en) |
FR (1) | FR3078947B1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102020006235A1 (en) * | 2020-10-09 | 2022-04-14 | Airbus Defence and Space GmbH | Air guiding arrangement for an aircraft with an integrated heat exchanger |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5988589A (en) * | 1996-07-17 | 1999-11-23 | Mowill; R. Jan | Air valve assembly including split-shaft and seal arrangement |
US7607308B2 (en) * | 2005-12-08 | 2009-10-27 | General Electric Company | Shrouded turbofan bleed duct |
GB0607771D0 (en) * | 2006-04-20 | 2006-05-31 | Rolls Royce Plc | A heat exchanger arrangement |
FR2902830B1 (en) * | 2006-06-27 | 2008-08-08 | Airbus France Sas | TURBOREACTOR FOR AIRCRAFT |
US7500493B2 (en) * | 2006-10-31 | 2009-03-10 | Visteon Global Technologies, Inc. | Tuning slide valve for intake manifold |
FR3015573B1 (en) * | 2013-12-19 | 2015-12-11 | Snecma | AIRCRAFT TURBOMACHINE COMPRISING A HEAT EXCHANGER OF THE PRE-COOLING TYPE |
FR3015569B1 (en) * | 2013-12-19 | 2019-01-25 | Safran Aircraft Engines | CARTER FOR A PROPULSIVE ASSEMBLY |
CA2950274A1 (en) * | 2014-05-29 | 2016-03-03 | General Electric Company | Turbine engine, components, and methods of cooling same |
US10260419B2 (en) * | 2015-07-31 | 2019-04-16 | General Electric Company | Cooling system |
US10563585B2 (en) * | 2016-03-02 | 2020-02-18 | United Technologies Corporation | Heat exchanger for gas turbine engine |
US10760492B2 (en) * | 2016-04-13 | 2020-09-01 | Raytheon Technologies Corporation | Cooling air architecture for compact size and performance improvement |
-
2018
- 2018-03-13 FR FR1852135A patent/FR3078947B1/en not_active Expired - Fee Related
-
2019
- 2019-02-08 US US16/271,300 patent/US20190285000A1/en not_active Abandoned
- 2019-02-11 EP EP19156326.1A patent/EP3539873B1/en active Active
- 2019-03-11 CN CN201910180585.2A patent/CN110271676A/en active Pending
Also Published As
Publication number | Publication date |
---|---|
EP3539873A1 (en) | 2019-09-18 |
EP3539873B1 (en) | 2020-12-23 |
CN110271676A (en) | 2019-09-24 |
FR3078947A1 (en) | 2019-09-20 |
US20190285000A1 (en) | 2019-09-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CA2621195C (en) | Turbofan provided with a pre-cooler | |
US10072577B2 (en) | Air cooler system for gas turbine engines | |
RU2483006C2 (en) | Aircraft power plant with hot air bleeding system | |
US20210108574A1 (en) | Self-adapting gas turbine firebox with variable geometry | |
EP3165449B1 (en) | Nacelle fluid drain | |
FR2734320A1 (en) | DEVICE FOR PREDICTING AND COOLING HOT AIR AT AN AIRCRAFT ENGINE | |
EP2543864A3 (en) | Aircraft propulsion assembly with a heat shield for thermal protection of a rear aerodynamic fairing of a pylon and a cooling method for the heat shield | |
CN104948286A (en) | Cooling method and device for engine core module | |
EP3249376B1 (en) | Device for conditioning the atmosphere in tests of internal combustion engines, method and use of said device | |
FR3078947B1 (en) | AIRCRAFT PROPULSION SYSTEM COMPRISING A DUAL-FLOW TURBOREACTOR AND A REDUCED AIR TAKE-OFF SYSTEM | |
FR3078367B1 (en) | TURBOMACHINE WITH A HEAT EXCHANGER IN THE SECONDARY VEIN | |
FR3028289B1 (en) | AIRCRAFT TURBOMACHINE COMPRISING AN AIR INTAKE BOX WITH VARIABLE AERODYNAMIC PROFILE | |
FR3014146B1 (en) | TURBOREACTOR NACELLE PUSH INVERTER COMPRISING TWO PIVOTING SHUTTERS THAT WILL ENCLOSE THE ANNULAR VEIN | |
KR20140118367A (en) | Engine Cooling System For Airplane | |
FR3078058B1 (en) | MOTORIZATION ASSEMBLY FOR AIRCRAFT COMPRISING LIFTING POINTS, AND TROLLEYS FOR SUPPORTING SUCH AN ASSEMBLY | |
RU161141U1 (en) | TWO-CIRCUIT GAS-TURBINE ENGINE | |
FR3089496B1 (en) | Boundary layer ingestion aircraft powertrain comprising an electric motor and a cooling system partly disposed in the outlet cone | |
ES2581281T3 (en) | Composite panel with integrated air intake | |
FR3076865B1 (en) | REAR ASSEMBLY OF AN AIRCRAFT TURBOREACTOR NACELLE INCLUDING A SLIDING GRID DRIVE INVERTER | |
FR3029240A1 (en) | AIR INLET AND FOREIGN BODY ARRANGEMENTS IN A PROPELLANT AIRCRAFT ASSEMBLY | |
JP2008539118A (en) | Low noise aircraft during takeoff and landing | |
US2129826A (en) | Fire protecting device for air cooled engines | |
US2103466A (en) | Aircraft construction | |
FR3080889B1 (en) | AIRCRAFT PROPULSION KIT INCLUDING A COLD AIR INTAKE DEVICE WITH VARIABLE AERODYNAMIC PROFILE | |
EP3992083B1 (en) | Aircraft including an engine and a system for cooling the engine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PLFP | Fee payment |
Year of fee payment: 2 |
|
PLSC | Publication of the preliminary search report |
Effective date: 20190920 |
|
PLFP | Fee payment |
Year of fee payment: 3 |
|
ST | Notification of lapse |
Effective date: 20211105 |